JPS6134079B2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a pilot device for a missile-type projectile, particularly a cannon projectile, or a rocket launched from an aircraft or the ground.

This type of projectile is aerodynamically steered by varying the angle of attack, which is the angle of deviation of the longitudinal axis of the projectile relative to the direction of flight, and uses a fixed wing supported by the atmosphere to steer it. Usually equipped.

The angle of attack imparted to a projectile is the result of the moment obtained by the setting of ailerons located at the front or rear of the projectile or by the excursion of the projectile's propulsion jet.

In any case, the ability of aerodynamic maneuvering is
It has the disadvantage of being limited by the delay in setting the angle of attack of the projectile since the projectile sets the angle of attack after a given order of steering system. In fact, this delay or time constant cannot be reduced below about 0.2 seconds. This is an obvious disadvantage for projectiles that are propelled at extremely high speeds, such as missiles.
Therefore, from a guidance standpoint, the performance that can be expected from such bullets is limited.

It is an object of the present invention to be able to reduce the aerodynamic drag of the bullet, to be able to maneuver outside the atmosphere, and to improve the angle of attack of the bullet by applying the lateral loads necessary for maneuvering the bullet to the center of gravity of the bullet. To provide a pilot device capable of correcting the trajectory of a bullet without changing the trajectory of the target flying object, and thereby significantly improving the response time constant of tracking the bullet to a change in the course of a target flying object.

According to the pilot device of the present invention, the above objects are:
A pilot device for a guided missile, comprising: - two gas generators arranged symmetrically in the missile on either side of the center of gravity of the missile for supplying a gas flow; - one of the two gas generators; a nozzle having a throat disposed therebetween; - conduit means disposed within the missile for directing the gas flow from the gas generator to the throat of the nord; - the center of gravity of the missile; and a plurality of injection ports located on the surface of the missile in the vicinity of a plane perpendicular to the longitudinal axis of the missile; - a lateral load due to the gas flow passing through the injection ports substantially on the center of gravity of the missile; a plurality of diverging conduits disposed within said missile and having a curved portion for connecting said nozzle to said jet orifice; a rotatably mounted vane having sides forming part of the wall of the diverging conduit; and means for rotating the vanes into the selected position.

According to a preferred embodiment, the pilot device of the invention is located close to the center of gravity of the missile.

It is understood that if the pilot arrangement is configured such that a lateral force acts on the center of gravity of the missile, the missile can correct its trajectory by the action of said force without changing the angle of attack. Good morning. As a result, the delay in setting the angle of attack or the aforementioned time constant is completely eliminated. This is a very important advantage of the device according to the invention.

According to a preferred embodiment, the pilot device of the invention comprises two gas generators arranged symmetrically on either side of the center of gravity of the missile and in communication with each other and coaxial with the longitudinal axis of the missile. and means for distributing or diverting the gas outside the missile in at least two directions symmetrical with respect to the longitudinal axis of the missile.

Under these conditions, the fuel loss is equal on both sides of the missile's center of gravity, so the outflow of gas from the two gas generators does not shift the missile's center of gravity. Such an arrangement is effective in maintaining balance of the missile during operation of the pilot system.

According to a possible embodiment of the pilot device according to the invention, the gas generator consists of two fuel tanks connected to each other by at least one longitudinal channel and which serves as a throat for the injection of combustion gases. Gas injection in the form of at least two diverging conduits, the nozzle network being formed in the wall of a tank adjacent to said passage and coaxial with the longitudinal axis of the missile and in two directions symmetrical with respect to the longitudinal axis of the missile. In communication with and complementary to the conduit, distribution means are mounted between the two tanks for directing the combustion gases in one or the other of said two symmetrical directions.

The response time of the gas distribution means and thus of the thrust generation is in the range of a few thousandths of a second. The response time of aerodynamic lift generation for conventional maneuvering systems is
The response time is extremely short compared to 0.2 seconds to 0.5 seconds or more. Also,
It is also possible to use compressed gas cylinders as gas generators. Again, the response time is extremely short, but the energy capacity is low.

According to a feature of the pilot device according to the invention, the distribution means include vanes in the form of vanes mounted rotatably about an axis perpendicular to the longitudinal axis of the missile, the vanes having an approximately triangular profile. and the top of the vane engages within the nozzle neck. The sides of the vanes extending from the top, together with the walls of the nozzle, form a conduit for injecting gas from the side of the missile to the outside of the missile. The vane is connected to vane rotation means that can swing the vane to one side or the other about the axis to direct the gas into one or the other injection conduit.

Further features and advantages of the pilot device of the invention will become apparent from the detailed description below. The accompanying drawings show some non-limiting embodiments of the device of the invention.

In the embodiment shown in FIGS. 1 to 5, a pilot device according to the invention is mounted on a projectile consisting of a missile 1. In the embodiment shown in FIGS. The pilot device 2 of the invention comprises means capable of generating a force in a direction perpendicular to the longitudinal axis XX of the missile 1 and distribution means for changing the direction of said force.

In the embodiment of FIG. 1, said means also include the energy means of the pilot system 2, located close to the center of gravity G of the missile 1. More specifically,
The energy means of the pilot device 2 include tanks 4a, 4b as two joint gas generators arranged symmetrically on either side of the center of gravity G and coaxially with the longitudinal axis XX of the missile 1. tank 4a,
4b communicate with each other and provide means for distributing or splitting the gas outside the missile 1 in two directions symmetrical with respect to the axis XX of the missile. As shown in FIG. 5, these directions are either perpendicular to the axis XX (F ₁ and F ₂ ) or perpendicular to the axis XX, as in the case of directions F ₃ and F ₄ .
tilted against. Corresponding forces (not shown) caused by reactions have corresponding directions. However, it may be considered that F ₁ is the force corresponding to the gas injection in the direction of the arrow F ₂ and F ₂ is the force corresponding to the gas injection in the direction of the arrow F ₁ .

The forces corresponding to F ₃ and F ₄ and inclined to the axis XX are the components perpendicular to the axis such as F ₁ and F ₂ shown in FIG. It has _a component force equal to and opposite to F ₅ of the same axis.

In the various cases of FIG. 5, the directions of these forces are:
It converges to one point on the axis XX consisting of the center of gravity G.

The gas generator has a built-in solid fuel 5.
It consists of two tanks 4a, 4b, which are interconnected by two parallel longitudinal passages 6, and a nozzle net 7 for discharging the combustion gases is located between the passages 6 in the side wall of the tank 4b for the missile 1. It is formed coaxially with the longitudinal axis XX. The nozzle neck 7 communicates with two conduits, ie, diverging conduits, which inject gas from a side opening 8 serving as an injection port, and the gas jet injected from the opening 8 is
It is injected as a bidirectional gas jet symmetrical about the longitudinal axis XX, for example in the direction of arrows F ₃ and F ₄ in FIG.

Furthermore, a distribution means 9 as shown in FIGS. 2 and 4 is installed between the two tanks 4a and 4b to direct the combustion gas in either of the two directions. In the embodiment of FIGS. 2 and 4, the distribution means 9 comprises vanes 11 in the form of vanes mounted rotatably about a pivot axis 12 perpendicular to the longitudinal axis XX of the missile. The vanes 11 have a generally triangular shape with a chamfered top 13 housed within the nozzle neck 7. The nozzle net 7 comprises two plates 10, which are integrated into the body 15 of the missile parallel to the longitudinal axis XX between two longitudinal passages 6 formed on either side of the longitudinal axis XX of the missile 1. 14 and two side plates 16. A side plate 16 is secured between the plates 10 and 14 within the space maintained between the plates 10 and 14 and the body 15 of the missile. Opposing edge 16a of side plate 16
The free space formed between them forms a nozzle net 7.

The side surface of the side plate 16 extending from the edge 16a and facing the vane 11, together with the side surface 11a as a corresponding side of the vane 11, is connected to the tank 4a,
A diverging conduit 17 is formed for injecting the combustion gas supplied from 4b. For this purpose, the side surfaces 11a extending from the top 13 have a certain degree of concave shape, so that the cross-section of these conduits widens in the direction from the nozzle neck 7 to the opening 8 as the injection orifice, effectively forming a diverging conduit. 17 is formed. In the embodiment of FIG. 2, said divergent conduits 17 are aligned with the longitudinal axis of the missile such that the direction of the gas jets that can be injected from these divergent conduits 17 is oblique to the axis XX.
Slanted to XX.

Vanes 11 are used to direct the gas supplied from the nozzle net 7 into one or the other of the diverging conduits 17.
is connected to a double-acting ram 18 as a vane rotating means for swinging the vane 11 to one side or the other side around the rotation axis 12. In the specific example shown in FIGS. 2 and 4, both ends of the double-acting ram 18 that swings the vane 11 are connected to a double-acting servo valve 19 equipped with two solenoids 21 at both ends by bend pipes 22, respectively. connected. That is, the central region of the pneumatic or hydraulic servo valve 19 is connected to two bend pipes 22 which open at opposite ends of an elongated chamber 23 . A piston 24 can reciprocate within the chamber 23. This piston 24 controls rotation of the vane 11.

The piston 24 consists of a bar that reciprocates within the chamber 23 in accordance with the control impulse-like fluid pressure supplied by one or the other of the solenoids 21;
The piston 24 has a central notch 25 in which a projection 26 integral with a web 27 secured to the opposite side 11b of the top 13 of the vane 11 engages.

Furthermore, the servovalve 19 is fitted with a longitudinal distribution rod 28 in a manner known per se;
Both ends of the rod 28 are fixed to the magnetic core of the solenoid 21. Excitation of solenoid 21 by electrical current pulls rod 28 in one direction or the other. Two cylindrical valve members 29 are provided in the central region of the rod 28, the spacing between the valve members 29 being determined by the activation of the solenoid 21.
Movement in one direction or the other is a bend pipe 2
The double acting ram 18 is adjusted to cause fluid discharge on the fluid discharge side of the double acting ram 18 by closing one or the other of the two. Four discharge ports 90 and 91 are formed in the body of the servo valve 19, and two discharge ports 90 and 91 are formed in the body of the servo valve 19.
is located close to the inlet of the bend pipe 22 and opens into the bend pipe 22. Further, the discharge port 91 is formed between the valve member 29 and the solenoid 21. Fluid is injected into the servo valve 19 through a central conduit 31 that opens between the valve members 29 .

When one solenoid 21 is energized, for example the left solenoid 21 in FIG. Close. Another bend pipe 22 is open. As a result, the pressure between both end faces of the piston 24 is unbalanced, and as a result, the piston 24 moves and rotates the vane 11 via the protrusion 26, as shown by the arrow in FIG. At the same time, the fluid in the double-acting ram 18 pushed back by the piston 24 flows out from the discharge ports 90, 91 connected to the bend pipe 22 and flows in the direction of the arrow in FIG.

According to a particularly important feature of the invention, the vanes 11 produced by the action of the combustion gases on the portion of the concave side surface 11a extending from the top 13 are directed in one direction (e.g. in the direction of arrow H in FIG. 4). Means is provided to substantially equalize the pivoting force and the opposing force caused by the gas acting on the portion of the side surface 11a spaced from the top 13. Fourth
With respect to the right side surface 11a of the vane 11 in the figure, said opposing forces are applied to the vane 11 in the direction indicated by arrow J.
The arrow J indicates a direction opposite to the rotation direction of the arrow H with respect to the rotation axis 12.

For this purpose, the surface of the side surface 11a located between the level of the rotation axis 12 (assuming that the vane 11 is vertical and the rotation axis 12 is horizontal) and the level of the top 13 is It is advantageous to arrange the axis of rotation 12 so that it is smaller than the surface of the side surface 11a located below the level of 12. This may generate a moment that rotates the vane 11 in the direction of arrow J. Divergent conduit 17 adjacent to opening 8
The gas pressure at the top 13 and the rotating shaft 12
less than the gas pressure between the level of . Rotation axis 12
By appropriate positioning of the side 1 of the vane 11
It will be appreciated that it is possible to maintain a practical balance between the opposing forces exerted by the gas on la and causing rotation of vane 11 in opposite directions.

This allows the vane 11 to rotate toward either of two possible positions relative to the side plate 16 even if perfect equilibrium is not achieved.
It is sufficient to apply a small impulse to the double-acting ram 18 of the vane 11, so that the gas can be directed into either of the two divergent conduits 17 in response to the rotation of the vane 11.

The operation and advantages of the pilot system as described above are described below.

- after the launch of the missile 1, the fuel 5 in the tanks 4a, 4b is ignited in a manner known per se, the combustion gases supplied from the tank 4a being fed into the longitudinal passage 6;
The gas is mixed with the gas produced by combustion of the fuel in the tank 4b. The mixed gas then flows into the nozzle network 7. This flow of combustion gas is indicated by arrows in FIG.

In order to direct the combustion gases in one of two possible directions, the distribution vane 11 is rotated on the pivot axis 12 until the top 13 abuts one of the edges 16a of the side plates 16.
It is sufficient to rotate it around the As a result, the diverging conduit 17 corresponding to the side plate 16 in contact with the vane 11 is closed. The gas thus passes through the unobstructed diverging conduit 17 and into the corresponding opening 8.
from the outside of the missile 1.

In order to place the vane 11 in one of the two possible positions mentioned above, the solenoid 21 corresponding to the desired position of the vane 11 is energized so that the double acting ram 1
Activate 8.

Lateral forces generated as described above (e.g. F
1, F2, or F3) act on the center of gravity of missile 1, and the trajectory of the missile is correspondingly modified by the acceleration transmitted to the missile as long as the force is maintained. . Since the forces that cause trajectory correction act precisely on the missile's center of gravity G,
Such trajectory corrections do not result in a substantial change in the missile's angle of attack. This is a very important advantage compared to conventional pilot systems.

The inclination of the gas jet after distribution with respect to the axis of the nozzle neck 7 (which axis preferably coincides with the longitudinal axis XX of the missile 1) is (in FIG. 5)
There is a wide variation between lines perpendicular to this axis, such as F1 or F2, and lines oblique to said axis, such as for example corresponding to arrow F6 shown in dotted lines in FIG.

In order to produce gas jets in different directions relative to the axis of the nozzle neck 7, it is necessary to adapt the shape of the diverging conduit 17 to the desired inclination of the gas jet.

If the gas jet is inclined with respect to the axis of the nozzle neck 7, ie the longitudinal axis XX of the missile 1, the gas jet has an axial component effective to produce a longitudinal thrust.

In each case, the longitudinal axis of the missile 1
It is advantageous to radiate the force around a point on XX. One point on the longitudinal axis XX is the center of gravity G in the above example.

The lateral force caused by the combustion of the fuel 5 is maintained as long as the combustion continues. Therefore, if it is desired to reduce the transverse force generated as described above to zero at a given moment, the vane 11 is swung about its axis after a very short period of time, and the gas jet is directed into one of the diverging conduits 17. Alternately divide the flow. The resultant force of the two opposing forces generated is zero. Therefore,
As long as vane 11 continues to swing, the missile remains on its new trajectory.

It is particularly advantageous to arrange the two fuel tanks 4a, 4b in symmetrical positions with respect to the center of gravity G of the missile. In fact, fuel burns the same on both sides of the center of gravity G. As a result, two fuel tanks 4a, 4b
An equal amount of fuel is reduced within, and the position of the center of gravity G remains unchanged as a result. Therefore, as long as the charge of fuel 5 continues to burn, the balance of the missile is maintained.

The arrangement of the rotation axis 12 of the vane 11 as described above, that is, the antagonistic forces exerted on the vane 11 by the gas and causing rotation of the vane 11 in opposite directions are substantially equal. The arrangement of the pivot axis 12 is very advantageous compared to known systems, especially needle systems. In fact, impulses of minute magnitude through a control device, such as the double-acting ram 18 or the device of FIG. 6, are sufficient to cause the rotation of the vane 11 in the desired direction.

Advantageously, the relative shape of the nozzle neck 7 and the top 13 of the vane 11 is such that the gas flow rate in the nozzle neck 7 remains constant regardless of the movement of the vane 11. In fact, no matter what position the vane 11 is in, the nozzle neck 7
The space through which the gas flows remains constant. This avoids undesirable vibrations that would cause pressure changes.

Another advantage of the pilot device of the invention is that there is no need to install a gas-tight joint at the pivot axis 12 of the vane 11. is engaged with the plate 14,
This is because all of the rotation shafts 12 fixed between the plates 14 and 10 are located within the pressurizing area.

The positioning control of the vane 11 may be performed intermittently or continuously. In the latter case, the distribution of the gas jet is effected in proportion to the angle of rotation of the vanes 11 between the side plates 16 by conventional control methods. In this case, the gas flows through the diverging conduit 1
It is simultaneously injected from two openings 8 of 7. When the tops 13 of the vanes 11 are equidistant from the edges of the side plates 16, the gas jets produce two equal and opposite lateral forces. As a result, the resultant force of the two forces is zero. In this way, the trajectory of the missile is maintained as long as the gas jets remain equal.

In the embodiment of FIG. 6, the means 33 for controlling the rocking of the vanes 34 include a transverse pipe 35 connected to two longitudinal passages 6. In the embodiment of FIG. The pipe 35 cooperates with means for alternately directing the gas within the pipe 35 to one or the other of the ends of the side surfaces 36 opposite the top 13 of the vane 34.

In the embodiment of FIG. 6, these means include a spool 37 that can be reciprocated within the central portion of the pipe 35 by the action of a control solenoid 38. The spool 37 crosses the solenoid 38 and
It consists of a metal rod with two cylindrical plungers 39 at both ends of a spool 37. plunger 39
has a size that can alternately block the entrance of either of the two conduits 41, 42, and
42 communicates with the pipe 35, and each ram 4
It has reached 3.

The ram 43 is attached to the side surface 3 of the vane 34 in order to rotate the vane 34 in a desired direction around the rotation axis 12.
6 includes a piston 44 with a push rod 45 that can act on the cooperating end of the piston 44. The piston 44 and push rod 45 assembly is preferably connected to a ball and socket joint that allows the end of the push rod 45 to maintain contact with the side surface 36 during rotation of the vane 34. Two orifices 92 located within the pipe 35 on either side of the solenoid 38 may allow gas to escape.

This distribution means can extract and use a portion of the power supplied by the pressurized gas as an energy source circulating in the passage 6 in the direction from the tank 4a to the tank 4b (arrow M).

The pressures exerted by the gas on the two plungers 39 are equal. Thus, when solenoid 38 is not energized, spool 37 is not subjected to any additional forces and vane 34 is in a central equilibrium position. solenoid 38
When energized, the spool 37 moves in one direction or the other so that one of the plungers 39 opens the inlet of the cooperating conduit 41 or 42. As a result, the pressure of the gas flowing into the opened conduit presses the piston 43, causing the push rod 45 to rotate the vane 34. On the other hand, the gas forced out by the further piston 43 exits from the conduit 41 and exits from the corresponding discharge orifice 92 .

The control means 33 have the advantage of directly using the force of the combustion gases to cause the rotation of the vanes 34.

In the embodiment of FIGS. 7-13, the pilot system of the invention includes means for distributing gas to the exterior of the missile. The means are arranged perpendicularly to each other and each includes two longitudinal axes XX of the missile 1.
includes four differently oriented conduits located in four different planes.

The distribution means shown in FIGS. 7 to 12 include vanes 46 cooperating with complementary fastening members 47 that are integral with the body of the missile 1. Vane 4
6 has four congruent branches 49 on the four sides of the bottom.
The branches are inclined with respect to the axis YY of the truncated pyramid 48 (in FIG. 9),
They are separated by 90 degrees from each other. The vane 46 is formed with a plane of symmetry that includes the axis of the truncated pyramid 48 . The truncated pyramid 48 preferably has a slightly convex end face 51 and is accommodated in a nozzle neck 52 formed inside the fixing member 47.

In this specific example, the cross-sectional shape of the nozzle neck 52 that cooperates with the head of the truncated pyramid 48 is square as shown in FIG. 12, so that the gas flow rate is maintained constant regardless of the position of the truncated pyramid 48. have relative dimensions.

The fixing member 47 has four branches 4 together with the vane 46.
9, and only three branches 53, 54, 55 are visible in FIG. The directions of these four diverging conduits generally correspond to the directions indicated by arrows F7 to F10 in FIG. 13 and corresponding to the axes of the four divergent conduits. Vanes 46 for selectively injecting gas into at least some of the diverging conduits.
Auxiliary means are provided which serve to control the rotation of the vane 46 about a point within the vane and which consist of a ball and socket joint 56 and an axial support 57 (FIG. 9).

The rotating means of the vane 46 will be described next.
First, the respective pistons 24 of the two assemblies consisting of the double-acting ram 18 and the servo valve 19 shown in FIGS. 2 and 4 are appropriately arranged so as to be perpendicular to the axis XX. Next, a web protrusion (not shown) appropriately provided on the vane 46 is appropriately engaged with each central notch 25 of the piston 24. By arranging the vane 11, the double-acting ram 18, and the servo valve 19 in this manner, the vane 46 can be moved in two orthogonal directions to control the opening and closing of the four divergent conduits formed by the fixed member 47 and the vane 46. It can be rotated.

The assembly of vane 46 and fixing member 47 thus constitutes the nozzle of the pilot device.

The ball and socket joint 56 is connected to the nozzle neck 5.
2 and on the longitudinal axis XX of the missile 1 to a support 57 coaxial with the axis XX.

According to a feature of this embodiment, each branch 49 consists of a trough-shaped member, as seen in particular in FIG. Branch 58 also consists of a trough-shaped or U-shaped member complementary to the trough-shaped member of branch 49. When the branches 49 and 58 approach each other in opposition, four diverging conduits for gas injection are formed, the same number as the vanes 46 and the fixing member 47 have, respectively. The nozzle neck 52 is formed in the center of the fixing member 47, that is, in the joining area of the four branches 58. In this way, the vane 46
constitutes a male half body which is fitted into a fixing member 47 forming a female half body.

A suitable shape as described above ensures that the gas-tightness of the distribution means is maintained most reliably, in order to completely prevent leakage in the other two nozzles when two nozzles discharge gas. Ru.

The nozzle and dispensing means shown in FIGS. 7-12 operate as follows.

Control of the vane 46 by rotating it around a fixed ball and socket joint 56 via mechanical, electrical, pneumatic or other powered devices known per se, connected to the control system of the missile. Do the following. In this way, the vane 46 is rotated, and the two side surfaces adjacent to the end surface 51 of the truncated pyramid 48 are
As shown in FIG. 2, it is brought into contact with two corresponding adjacent side surfaces of a rectangular nozzle neck 52. This position is also closer to the position shown in FIG. In such a state, the tanks 4a, 4
When the fuel 5 of b is ignited, the combustion gas flows through the vane 4
6, namely, in the case of FIG. 10, the two divergent conduits 54, 55.

Therefore, the gas is 2 in two perpendicular planes.
It is ejected from the missile through the directions (arrows F11 and F12 in FIG. 12). The gas flow rates in these two directions are substantially equal, and the resultant force F13 is formed by the diagonals of a rectangle whose sides are F11 and F12.
has. Therefore, the missile moves in the opposite direction of the resultant force F13 due to the reaction. If it is desired to stabilize the missile on a new trajectory, the means for pivoting the vane 46 places the vane 46 in a central position where the four divergent conduits are not closed, as shown in FIG. In this case, the gas exits simultaneously at equal flow rates from the four divergent conduits formed by the branch pairs 49, 58, so that the resultant of the four correlated thrust forces is zero.

It is of course also possible to configure the diverging conduit for gas injection so that the gas is discharged in four directions perpendicular and orthogonal to the longitudinal axis XX of the missile 1, as indicated by the arrows in FIG. The husband's axial component of these four thrust forces is zero.

The variant embodiment shown in FIGS. 14-16 shows a distribution means comprising vanes 59 having a conical profile. The central part of the vane 59 is coaxial with the longitudinal axis XX of the missile 1, and the chamfered apex 61 of the vane 59 is connected to the corresponding circular nozzle neck 62.
engaged within.

Hollow vane 59 connects ball and socket joint 5
6 inside the cone via a ball-and-socket joint 63 fixed to an axial support 67.
It is attached so that it can rotate freely around a point. ball·
Control means similar to those provided on vane 46 may be used to rotate conical vane 59 about socket joint 63.

When the head 61 of the vane 59 is positioned to engage the center of the circular nozzle neck 62 as shown in FIG.
It forms an annular layer coaxial with XX, surrounds the entire outer circumference of the vane, and flows out. Openings are formed in the portion of the circumference of the missile adjacent to the bottom of the vane 59 so that gas can be injected virtually continuously over the entire circumference of the missile 1. Therefore, as shown in FIG.
The body of the missile 1 has an annular break 64 . A connecting rib 65 of sufficient strength ensures the connection between the two parts of the missile 1.

When vane 59 is pivoted about ball and socket joint 63 to bring vane 59 close to the edge of nozzle neck 62, for example to the position shown in FIG.
flows out from. The gas flow rate is not equal from one end of this horseshoe-shaped space to the other, and
The gas flow rate is highest in the region where the distance between the edge of head 61 and the circumference of head 61 is greatest. head 6
1 and nozzle neck 62, a very low gas flow rate is maintained on both sides of the line of contact between nozzle neck 62. In this case, the resultant thrust passes through the region where the spacing between the edge of the nozzle neck 62 and the head 61 is maximum. Therefore, the resultant force is in the direction opposite to the direction of arrow F14. Vane 5 continuously around ball and socket joint 63
By rotating 9, an adjustable annular gas layer is formed.

Continuous control of the vane 59 and other vane embodiments is achieved by means of two intersecting vane position sensors (e.g. two potential differential ).

FIG. 17 shows another modification of the device of FIG. 4.
In this modification, the control of the vane 11 is
This is done via a single position detector 94 located close to 1.

The detector is connected via a connection line (not shown) to a member 95 that includes a piston 96 that is integrated with the piston 24 via a rod 97. member 95
is connected to comparator 98. The comparator itself is connected on the one hand to an electric vane 11 position control system (not shown) and on the other hand to the control solenoid 21 of the servo valve 19 via an amplifier 99 (connection 10
0 and 101).

Therefore, the position control of the vane 11 is performed according to the result of the comparison between the signals received by the comparator 98.
An electrical impulse is delivered to either of the servo valves 19 via an amplifier 99. The position of the vane 11 is therefore controlled by the control system of the missile 1.

The invention is not limited to the various embodiments described, but may include numerous variations either in the examples described or in possible alternatives. Therefore, the pilot device may be mounted at a location remote from the missile's center of gravity, for example at the front of the missile.
In this case, the angle of attack of the missile can be changed during the trajectory of the missile by actuation of the device. This means that
In some cases this is desirable, for example when it is desired to avoid protruding guide wings to the outside of the missile, such as in glider-type guides, which has the advantage of preserving the aerodynamic shape of the missile.

Furthermore, it is also possible to use gas generators other than tanks containing stationary fuel, for example compressed gas tanks. In addition, in order to ensure the balance of a vane that distributes gas only to two divergent conduits, such as the vane 11 in FIG. Examples are also possible. However, the creation of this variant is technically more difficult than properly positioning the axis of rotation to maintain a balance of antagonistic forces. Furthermore, it is also possible to provide only one or several connecting passages between the fuel tank or more broadly between two gas generators.

According to the pilot device of the present invention, the aerodynamic resistance of the missile can be reduced because the guide vanes for changing the angle of attack of the missile can be omitted, and the reaction force from the air for modifying the trajectory of the missile can be reduced. Since this is not necessary, the missile can be maneuvered outside the atmosphere, and by applying the lateral load necessary for missile maneuvering to the missile's center of gravity, the trajectory of the missile can be modified without changing the missile's angle of attack. Therefore, the response time constant of missile tracking to a change in the course of a target flying object can be significantly improved compared to a missile that is steered by changing the missile's angle of attack, and as a result, hit accuracy is significantly improved.

[Brief explanation of the drawing]

FIG. 1 is a schematic side view in partial longitudinal section of a missile equipped with the pilot device of the present invention, and FIG. 2 is an enlarged partial elevational view taken along the line of FIG. 3 of a first embodiment of the pilot device of the present invention. , FIG. 3 is a general sectional elevational view of the pilot device along the direction K of FIG. 2, and FIG. 5 is a schematic explanatory view showing the direction of the gas jet that can be generated by the pilot device of FIGS. 1 to 4, and FIG. FIG. 4 is a partial sectional elevational view similar to FIG. 4 of a second embodiment of the distribution means and its control device which can be mounted on the pilot device of FIG. 3, and FIG. 7 shows the same point on the longitudinal axis of the missile. FIG.
FIG. 9 is an axial cross-sectional view showing the fixing member of FIG. 8 and the vane of FIG. 7 engaged with the fixing member; FIG. , FIG. 10 is a perspective view showing a combination of the vane and fixing member shown in FIGS. 7 to 9, and is an explanatory view in which gas is arranged to flow out from two of the four directions, and FIG. is a perspective view of the combination shown in Fig. 10 as seen from the nozzle neck side;
Figure 2 is an elevational view of the nozzle neck showing the direction of gas outflow when the vane is in the position shown in Figures 10 and 11, and Figure 13 is an elevational view of the nozzle neck showing the direction in which the gas jet flows out in the specific example of Figures 7 to 12. FIG. 14 is a perspective view of a third embodiment of the gas distribution vanes of the device according to the invention, arranged so that the gases form a rotating layer about the long axis of the missile; FIG. FIG. 15 is a schematic side view showing the circumference of the missile of the gas injection conduit portion used in the modification of the vane shown in FIG. 14 to discharge gas over the entire circumference of the projectile. , FIG. 16 is an elevational view similar to FIG. 12 showing the vanes pressed against the wall of the nozzle neck to force gas to escape from the unoccluded direction, and FIG. 17 is a modified embodiment of the control device of FIG. 4. It is an explanatory diagram. 1...Missile, 2...Pilot device, 4
a, 4b... Tank, 7... Nozzle net, 9...
...distribution means, 11... vane, 10, 14... plate.

Claims (1)

Claims: 1. A pilot device for a guided missile, comprising: - two gas generators arranged symmetrically in the missile on either side of the center of gravity of the missile for supplying a gas flow; - a nozzle having a throat located between the two gas generators; - conduit means located within the missile for directing the gas flow from the gas generator to the throat of the nozzle; a plurality of injection ports located on the surface of the missile in the vicinity of a plane containing the center of gravity of the missile and perpendicular to the longitudinal axis of the missile; - a lateral load due to the gas flow passing through the injection ports is substantially a plurality of diverging conduits disposed within the missile so as to be directed toward the center of gravity of the missile and having a curved portion for connecting the nozzle to the injection port; - a portion at the throat of the nozzle; a rotatably mounted vane having sides that are housed in the conduit and form part of the wall of the diverging conduit; means for controlling the dispensing and rotating said vane to a selected position. 2. The two gas generators are substantially identical, and the two gas generators are arranged coaxially with the longitudinal axis of the missile and equidistant from the center of gravity of the missile. The device described in. 3. The method according to claim 1 or 2, wherein the conduit means comprises a plurality of longitudinal conduits arranged in the vicinity of the nozzle and for connecting the two gas generators in parallel. Device. 4. The device according to claim 1, wherein each of the two gas generators comprises a combustion chamber and a solid propellant within the combustion chamber. 5. The plurality of injection ports are comprised of two injection ports that are opposed to each other in the diametrical direction of the missile, the nozzle is comprised of a side wall that partially forms the diverging conduit, and the rotatably mounted vanes are arranged in a direction of the missile. arranged for rotation about an axis perpendicular to the longitudinal axis, said vane having a generally triangular profile with an apex partially housed within a throat of said nozzle; extending from the top to form the diverging conduit with a nozzle, and means for rotating the vanes swinging the vanes laterally to distribute the gas flow to one or the other of the two injection ports, respectively. 5. A device according to any one of claims 1 to 4, which is arranged to cause 6 The force that causes the blade to rotate in one of the lateral directions due to the passage of the gas flow along a portion of the side portion adjacent to the top portion is applied along a portion of the side portion opposite to the top portion. The sides of the vane extend from the top contained within the throat of the nozzle so as to be substantially equal to the force that causes the vane to pivot in the other lateral direction due to the passage of the gas stream. It has a shape that
6. The device according to claim 1, wherein the rotation axis of the blade is arranged so as to cancel out the two forces that rotate the blade. 7. Claims 1 to 6, wherein the device includes an energy source provided within the missile for actuating the means for rotating the blades, the energy source comprising the gas generator. The device described in any of the above.